Fiber-fed Pulsed Plasma Thruster for High Total Impulse
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Solution Overview
Problem
Classic pulsed plasma thruster (PPT) technology is limited by its high mass and small propellant load, making it unsuitable for primary propulsion applications such as orbit change and de-orbiting, and it lacks the capability for high total impulse and low specific mass.
Innovation Solution
The Fiber-fed Pulsed Plasma Thruster (FPPT) addresses these limitations by replacing the traditional spring-fed propellant feed system with a motor-driven fiber feed system and incorporating a highly parallel ceramic capacitor bank, which significantly reduces system specific mass and enables higher propellant throughput.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If traditional spring-fed propellant feed system is used, then system simplicity is maintained, but propellant throughput is limited and total impulse is reduced
Solution Approach 1:
The patent replaces the traditional spring-fed mechanical feed system with a motor-driven fiber feed system. The motor-driven mechanism pulls fiber propellant from a spool through the anode at controlled rates, enabling precise regulation of propellant throughput and significantly higher total impulse capability while maintaining system manageability through electronic control rather than complex mechanical linkages.
Solution Approach 2:
The patent introduces a dynamic propellant feed mechanism where the motor-driven fiber feed system can adjust feed rates in real-time based on mission requirements. This dynamic control allows the system to optimize propellant delivery for different operational modes (e.g., high thrust vs. high specific impulse) whereas the traditional spring-fed system provides fixed, unregulatable feed rates.
2Quantity of substance
If traditional PPT design is used, then manufacturing simplicity is maintained, but specific mass is high and total impulse is limited
Solution Approach 1:
The patent changes the propellant storage parameter from traditional solid propellant bars to spooled fiber propellant. This parameter change enables significantly higher propellant mass to be stored in a compact configuration, increasing total impulse capability while the fiber format allows for more efficient packaging and reduced overall system mass compared to traditional rigid propellant storage containers.
Solution Approach 2:
The patent employs composite material strategies in the thruster construction, utilizing advanced materials for the anode, cathode, and structural components to reduce overall system mass. The fiber propellant itself (PTFE) is used in a composite configuration with the motor-driven feed system, creating an integrated propellant-delivery system that achieves higher performance-to-mass ratio.
3Adaptability or versatility
If traditional PPT is used for precision pointing, then reliability is maintained, but capability for primary propulsion applications is insufficient
Solution Approach 1:
The patent designs the motor-driven fiber-fed PPT system to be universally applicable across multiple propulsion scenarios. The same basic thruster architecture can support both precision pointing applications (using low thrust, high specific impulse modes) and primary propulsion applications (using high thrust modes for orbit change and de-orbiting), thereby achieving multi-functionality while maintaining the reliability of proven PPT technology.
Solution Approach 2:
The patent enables dynamic adaptation between different operational modes through the motor-driven feed system. By controlling the fiber feed rate and pulse parameters, the system can switch between precision pointing mode (low thrust, high accuracy) and primary propulsion mode (high thrust, high delta-V), providing versatility across mission requirements while maintaining reliable operation through electronic control rather than mechanical reconfiguration.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The FPPT achieves a higher total impulse per unit volume and lower specific mass compared to traditional PPT systems, enabling more efficient and cost-effective propulsion for small satellites, including orbit raising, de-orbiting, and inclination changes.
Implementation Method 1
a power processing unit electrically connected in parallel to a capacitor bank... configured to lower the equivalent series resistance to raise a pulse current
Implementation Method 2
an igniter fitted through an opening in the cathode... configured to expel electrons toward the anode region to ignite a primary high current discharge
Implementation Method 3
creating a plasma that vaporizes the fiber propellant at the anode exit end
Implementation Method 4
the vaporizing fiber propellant combines with the high current discharge to create a partially or fully ionized plasma
Implementation Method 5
produce a predominantly j×B thrust... electromagnetically and electrothermally accelerated outward from the nozzle region
Implementation Method 6
create a partially or fully ionized plasma electromagnetically and electrothermally accelerated outward from the nozzle region to produce the predominantly j×B thrust
Data Source
AI summary
A Fiber-fed Pulsed Plasma Thruster (FPPT) has an anode, a coaxial insulator, and a fiber propellant feed system. At least two cathodes insulated from each other are configured about the coaxial insulator to define an interior profile shaped into a nozzle region. At least one igniter fitted through each cathode. Wherein when the igniters are triggered, the igniters expel electrons toward the anode to ignite a primary high energy discharge between the anode and the cathodes thereby creating a plasma that vaporizes the fiber propellant. The dissociated fiber propellant combines with the primary high energy discharge to create a partially or fully ionized plasma, that is electromagnetically and electrothermally accelerated to produce predominantly {right arrow over (j)}×{right arrow over (B)}{right arrow over (j)}×{right arrow over (B)} thrust.